On porous liquid propellant rocket engine injectors

Johannes Lux; Dmitry Suslov; Oskar Haidn

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On porous liquid propellant rocket engine injectors

机译：在多孔液体推进剂火箭发动机喷油器上

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摘要

A novel injection concept for cryogenic liquid propellant rocket engines has been tested and verified successfully using an optically accessible combustion chamber. The injector consists of a porous faceplate made from sinter metal and five LOX posts arranged in a classical parallel showerhead configuration. While liquid oxygen is injected at similar velocities known from typical coaxial injector elements, the fuel enters the combustion chamber at much lower velocities. The flame stabilization for both LOX/H_2 and LOX/CH_4 propellant combination has been investigated at sub-, near-, and supercritical pressures.

机译：低温液体推进剂火箭发动机的新型喷射概念已经通过使用光学通道燃烧室进行了测试和验证。喷油器由一块由烧结金属制成的多孔面板和五个以经典平行喷头形式排列的LOX柱组成。当液态氧以典型同轴喷射器元件已知的相似速度喷射时，燃料以低得多的速度进入燃烧室。已经在低于，接近和超临界压力下研究了LOX / H_2和LOX / CH_4推进剂组合的火焰稳定性。

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来源
《Aerospace science and technology》 |2008年第6期|p.469-477|共9页
作者
Johannes Lux; Dmitry Suslov; Oskar Haidn;
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作者单位

German Aerospace Center (DLR), Institute of Space Propulsion, 74239 Lampoldshausen, Germany;

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收录信息美国《科学引文索引》(SCI);美国《工程索引》(EI);
原文格式 PDF
正文语种 eng
中图分类航空、航天;
关键词
high pressure; liquid propellant rocket engines; LOX methane hydrogen combustion; porous injection; subcritical supercritical;

机译：高压;液体推进剂火箭发动机;LOX甲烷氢燃烧;多孔注入;亚临界超临界;

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专利

1. Propellant Injector Influence on Liquid-Propellant Rocket Engine Instability [J] . Pavel P. Popov, William A. Sirignano, Athanasios Sideris Journal of propulsion and power . 2015,第1期

机译：推进剂喷油器对液体推进剂火箭发动机不稳定性的影响
2. EXPERIMENTAL INVESTIGATION OF CHARACTERISTICS OF A DOUBLE-BASE SWIRL INJECTOR IN A LIQUID ROCKET PROPELLANT ENGINE [J] . Fathollah OMMI, Koros NEKOFAR, Amir KARGAR, Thermal science . 2010,第2期

机译：液体火箭发动机双基旋流喷枪特性的实验研究
3. Experimental investigation of characteristics of a double-base swirl injector in a liquid rocket propellant engine [J] . Ommi Fathollah, Nekofar Koros, Kargar Amir, Thermal science . 2010,第2期

机译：液体火箭发动机双基涡旋喷油器特性的实验研究
4. Experimental Investigation of Porous Injectors for Liquid Propellant Rocket Engines [C] . J. Lux, D. Suslov, O. Haidn AIAA/ASME/SAE/ASEE Joint Propulsion Conference Exhibit . 2008

机译：液体火箭发动机多孔喷射器的实验研究
5. Primary atomization study of a swirl coaxial liquid propellant rocket injector. [D] . Rahman, Shamim Aejaz. 1997

机译：涡旋同轴液体推进剂火箭喷射器的初步雾化研究。
6. Examination of the liver in personnel working with liquid rocket propellant [O] . Palle Petersen, Erik Bredahl, Ove Lauritsen, 1970

机译：液体火箭推进剂工作人员的肝脏检查
7. Heat exchange efficiency in porous structural elements of liquid-propellant rocket engines [O] . Ф.В. Пелевин, Н.И. Авраамов, С.А. Орлин, 2013

机译：液体推进剂火箭发动机多孔结构元件的热交换效率
8. An experimental correlation of the nonreactive properties of injection schemes and combustion effects in a liquid-propellant rocket engine. part 1- the application of nonreactive-spray properties to rocket-motor injector design [R] . Rupe, J. H. 1965

机译：液体推进剂火箭发动机喷射方案非反应特性与燃烧效应的实验关联。第1部分 - 非反应喷涂特性在火箭发动机喷射器设计中的应用

On porous liquid propellant rocket engine injectors

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